Supersonic flow control

Verma, Shashi B.; Hadjadj, A.

doi:10.1007/s00193-015-0587-y

Cited by 25 publications

(10 citation statements)

References 59 publications

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“…The working principle of these devices is through the generation of streamwise vortices (co-or counter-rotating) to improve the overall structure of the incoming boundary layer. A detailed comprehensive view of the various control techniques, both active and passive, that have been used to control supersonic shock-wave/boundary-layer interactions (SWBLI) can be found in [41]. Past studies also report that although the active devices have the added flexibility to switch on and off on-demand [29], suppress specific flow frequencies [41] and reduce device drag when not in use, the system cost and the complexities associated with them makes it difficult to implement and maintain [22].…”

Section: Introductionmentioning

confidence: 99%

“…A detailed comprehensive view of the various control techniques, both active and passive, that have been used to control supersonic shock-wave/boundary-layer interactions (SWBLI) can be found in [41]. Past studies also report that although the active devices have the added flexibility to switch on and off on-demand [29], suppress specific flow frequencies [41] and reduce device drag when not in use, the system cost and the complexities associated with them makes it difficult to implement and maintain [22]. The mechanical devices, on the other hand, are low cost, simple, and rugged in design [36,37,42] making them potential candidates for use as flow control devices in air intakes.…”

Section: Introductionmentioning

confidence: 99%

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Control of a Mach reflection-induced interaction using an array of vane-type vortex generators

Verma

Manisankar

2017

Shock Waves

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An experimental investigation was conducted to control a Mach reflection (MR)-induced flow separation in a Mach 2.05 flow using a 18 • shock generator (SG). The study was extended to four SG exit heights (g/w) of 0.87, 0.81, 0.725, and 0.66 primarily to study its effect on the extent of flow separation as well as on Mach stem height, with and without control. Two vane-type vortex generator configurations, namely the ramp vane (RV) with device heights h/δ = 0.3, 0.5, 0.8, and 1.0 and the rectangular vane (RRV) with h/δ = 0.3 and 0.5, were studied for control. Each control device array was implemented 10δ upstream of the separation location for no control. For stable MR interactions (i.e., g/w = 0.87, 0.81), the extent of separation and the reattachment shock strength are seen to decrease with increase in RV height (with h/δ = 1.0 device showing 17% reduction). However, for unstable MR condition (i.e., g/w = 0.725), RV devices of h/δ = 0.8 and 1.0 become ineffective. The RRV2 device (h/δ = 0.5), on the other hand, was found to be more effective in reducing the extent of separation in both the stable (31%) and unstable (24%) MR conditions. The effectiveness of each control device is also accompanied with an increase in height of the Mach stem. This is, however, not seen as a serious limitation since in such strong interactions it is more important to prevent or avert an intake unstart condition. The separation shock unsteadiness or the σ max /P w value, on the Communicated by C.-Y. Wen and A

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Control of a Mach reflection-induced interaction using an array of vane-type vortex generators

Verma

Manisankar

2017

Shock Waves

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“…The passive approach, on the other hand, uses fixed mechanical devices projecting into the boundary layer, such as vanes in co-or counter-rotating configuration, microramps, etc., to initiate a similar effect. Verma and Hadjadj [25] give a detailed comprehensive view of the various flow control techniques used in SWBLIs. Although the active control has the added advantage of being switched on or off as per requirement [19,20], they do require input of extra energy for their activation and, hence, may increase installation and maintenance costs.…”

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confidence: 99%

Control of Incident Shock-Induced Separation Using Vane-Type Vortex-Generating Devices

Verma

Manisankar

2018

AIAA Journal

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An experimental investigation was conducted to control an incident shock-induced boundary-layer separation associated with a 14 deg shock generator in a Mach 2.05 flow. Two vane-type configurations, namely the triangular (h∕δ 0.3, 0.5, 0.8, 1.0) and the rectangular (h∕δ 0.5) designs, were studied. An array of each control device was tested for three control locations of X∕δ 5, 10, and 15. The control location of 5δ is seen to show the maximum reduction in separation length for each device tested. For the rectangular-vane device (h∕δ 0.5), a maximum reduction of 38% in separation length is observed, followed by the triangular-vane devices of h∕δ 0.8 and 1.0, each of which shows a 32% reduction, and finally, h∕δ 0.5 with 18%. The effectiveness of these devices to control separation is, however, seen to decrease with increase in X∕δ. In terms of separation shock unsteadiness, the maximum rms value for X∕δ 5δ shows the highest value for each control device, and this value decreases with increase in control location. At X∕δ 15, both the rectangular vane (h∕δ 0.5) and triangular vane (h∕δ 0.8;1.0) show a 50% reduction in maximum rms value, whereas it decreases to 30% at X∕δ 10 for these devices.

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“…Although it is impossible to eliminate shock-boundary layer interactions from these highspeed flowfields, it is essential to alleviate or reduce its undesirable effects for better performance and reliability of these vehicles. Many techniques (18) have been put forth by researchers in the past to mitigate and possibly eliminate the shock-induced flow separation such as steady (19,20) and pulsating (21) microjet actuators, plasma actuators (22,23) , shock control bumps (24) , aerodynamic bleed (25) , magnetohydrodynamic systems, (26) etc. A large number of these flow control techniques are employed to energize the low momentum fluid of the boundary layer that is close to the wall, thereby enabling it to better resist the adverse pressure gradient.…”

Section: Introductionmentioning

confidence: 99%

Effect of microramps on flare-induced shock – boundary-layer interaction

2019

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The ability of microramps to control shock - boundary layer interaction at the vicinity of an axisymmetric compression corner was investigated computationally in a Mach 4 flow. A cylinder/flare model with a flare angle of 25° was chosen for this study. Height (h) of the microramp device was 22% of the undisturbed boundary layer thickness (δ) obtained at the compression corner location. A single array of these microramps with an inter-device spacing of 7.5h was placed at three different streamwise locations viz. 5δ, 10δ and 15δ (22.7h, 45.41h and 68.12h in terms of the device height) upstream of the corner and the variations in the flowfield characteristics were observed. These devices modified the separation bubble structure noticeably by producing alternate upwash and downwash regions in the boundary layer. Variations in the separation bubble’s length and height were observed along the spanwise (circumferential) direction due to these devices.

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Supersonic flow control

Cited by 25 publications

References 59 publications

Control of a Mach reflection-induced interaction using an array of vane-type vortex generators

Control of a Mach reflection-induced interaction using an array of vane-type vortex generators

Control of Incident Shock-Induced Separation Using Vane-Type Vortex-Generating Devices

Effect of microramps on flare-induced shock – boundary-layer interaction

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